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HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 AIRFOIL (hq259-il)
Reynolds number: 500,000
Max Cl/Cd: 88.43 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259-il-500000-n5.txt
Download as CSV file: xf-hq259-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4000   0.08360   0.08143  -0.0350   1.0000   0.0077
  -8.250  -0.4012   0.08015   0.07802  -0.0362   1.0000   0.0077
  -8.000  -0.4065   0.07645   0.07437  -0.0372   1.0000   0.0078
  -7.750  -0.4172   0.07321   0.07119  -0.0373   1.0000   0.0079
  -7.500  -0.4052   0.06654   0.06454  -0.0472   0.9893   0.0079
  -7.250  -0.3845   0.05814   0.05603  -0.0605   0.9803   0.0080
  -7.000  -0.3633   0.05114   0.04887  -0.0694   0.9730   0.0082
  -6.750  -0.3427   0.04500   0.04251  -0.0750   0.9631   0.0081
  -6.500  -0.3199   0.04179   0.03912  -0.0777   0.9550   0.0063
  -6.250  -0.3009   0.03571   0.03270  -0.0808   0.9439   0.0055
  -6.000  -0.2857   0.02480   0.02101  -0.0811   0.9308   0.0039
  -5.750  -0.2621   0.02238   0.01820  -0.0809   0.9219   0.0037
  -5.500  -0.2382   0.02031   0.01580  -0.0807   0.9135   0.0037
  -5.000  -0.1891   0.01655   0.01135  -0.0799   0.8979   0.0036
  -4.750  -0.1638   0.01488   0.00936  -0.0794   0.8910   0.0036
  -4.500  -0.1381   0.01360   0.00784  -0.0790   0.8833   0.0036
  -4.250  -0.1128   0.01219   0.00621  -0.0784   0.8764   0.0037
  -4.000  -0.0874   0.01108   0.00493  -0.0779   0.8690   0.0039
  -3.750  -0.0613   0.01029   0.00398  -0.0776   0.8622   0.0044
  -3.500  -0.0345   0.00983   0.00343  -0.0773   0.8552   0.0051
  -3.250  -0.0073   0.00951   0.00298  -0.0772   0.8486   0.0058
  -3.000   0.0200   0.00927   0.00267  -0.0770   0.8414   0.0070
  -2.750   0.0475   0.00902   0.00231  -0.0769   0.8344   0.0088
  -2.500   0.0750   0.00885   0.00206  -0.0767   0.8267   0.0108
  -2.250   0.1024   0.00860   0.00185  -0.0766   0.8182   0.0288
  -2.000   0.1295   0.00838   0.00169  -0.0765   0.8095   0.0621
  -1.750   0.1567   0.00812   0.00153  -0.0764   0.8005   0.1087
  -1.500   0.1828   0.00744   0.00138  -0.0766   0.7922   0.2787
  -1.250   0.2071   0.00657   0.00134  -0.0765   0.7845   0.5450
  -1.000   0.2343   0.00647   0.00133  -0.0763   0.7755   0.5914
  -0.750   0.2611   0.00640   0.00133  -0.0760   0.7653   0.6372
  -0.500   0.2874   0.00634   0.00134  -0.0755   0.7534   0.6856
  -0.250   0.3141   0.00634   0.00134  -0.0752   0.7397   0.7085
   0.000   0.3411   0.00636   0.00132  -0.0749   0.7249   0.7220
   0.250   0.3684   0.00640   0.00131  -0.0747   0.7117   0.7317
   0.500   0.3957   0.00644   0.00131  -0.0746   0.6994   0.7415
   0.750   0.4229   0.00648   0.00132  -0.0744   0.6863   0.7512
   1.000   0.4498   0.00653   0.00134  -0.0741   0.6704   0.7611
   1.250   0.4765   0.00661   0.00136  -0.0738   0.6527   0.7717
   1.750   0.5295   0.00676   0.00146  -0.0732   0.6157   0.7951
   2.000   0.5555   0.00686   0.00152  -0.0728   0.5931   0.8082
   2.250   0.5808   0.00699   0.00159  -0.0723   0.5634   0.8228
   2.500   0.6051   0.00718   0.00169  -0.0716   0.5262   0.8397
   2.750   0.6289   0.00737   0.00180  -0.0708   0.4898   0.8609
   3.000   0.6519   0.00751   0.00196  -0.0698   0.4570   0.8965
   3.250   0.6853   0.00775   0.00211  -0.0711   0.4153   1.0000
   3.500   0.7105   0.00809   0.00230  -0.0708   0.3805   1.0000
   3.750   0.7352   0.00846   0.00251  -0.0704   0.3412   1.0000
   4.000   0.7597   0.00887   0.00274  -0.0700   0.3013   1.0000
   4.250   0.7845   0.00924   0.00301  -0.0696   0.2720   1.0000
   4.500   0.8097   0.00958   0.00326  -0.0693   0.2479   1.0000
   4.750   0.8351   0.00988   0.00350  -0.0690   0.2292   1.0000
   5.000   0.8606   0.01017   0.00376  -0.0688   0.2117   1.0000
   5.250   0.8841   0.01068   0.00407  -0.0682   0.1739   1.0000
   5.500   0.9058   0.01137   0.00447  -0.0675   0.1241   1.0000
   5.750   0.9297   0.01183   0.00486  -0.0670   0.1005   1.0000
   6.000   0.9519   0.01247   0.00531  -0.0663   0.0669   1.0000
   6.250   0.9736   0.01317   0.00584  -0.0656   0.0377   1.0000
   6.500   0.9922   0.01428   0.00671  -0.0643   0.0039   1.0000
   6.750   1.0157   0.01477   0.00727  -0.0636   0.0029   1.0000
   7.000   1.0390   0.01528   0.00786  -0.0629   0.0026   1.0000
   7.250   1.0617   0.01585   0.00853  -0.0622   0.0023   1.0000
   7.500   1.0837   0.01649   0.00929  -0.0613   0.0022   1.0000
   7.750   1.1049   0.01720   0.01012  -0.0603   0.0021   1.0000
   8.000   1.1248   0.01807   0.01116  -0.0591   0.0021   1.0000
   8.250   1.1432   0.01905   0.01228  -0.0578   0.0020   1.0000
   8.500   1.1605   0.02009   0.01345  -0.0563   0.0020   1.0000
   8.750   1.1760   0.02128   0.01478  -0.0546   0.0020   1.0000
   9.000   1.1894   0.02263   0.01628  -0.0526   0.0020   1.0000
   9.250   1.2026   0.02394   0.01773  -0.0506   0.0020   1.0000
   9.500   1.2141   0.02538   0.01932  -0.0484   0.0020   1.0000
   9.750   1.2231   0.02688   0.02097  -0.0459   0.0020   1.0000
  10.000   1.2290   0.02854   0.02280  -0.0431   0.0020   1.0000
  10.250   1.2346   0.03017   0.02460  -0.0403   0.0020   1.0000
  10.500   1.2383   0.03202   0.02663  -0.0376   0.0020   1.0000
  10.750   1.2368   0.03449   0.02932  -0.0347   0.0019   1.0000
  11.000   1.2323   0.03731   0.03238  -0.0320   0.0019   1.0000
  11.250   1.2278   0.04011   0.03539  -0.0297   0.0019   1.0000
  11.500   1.2340   0.04140   0.03686  -0.0285   0.0018   1.0000
  11.750   1.2369   0.04324   0.03886  -0.0274   0.0017   1.0000
  12.000   1.2349   0.04584   0.04164  -0.0264   0.0017   1.0000
  12.250   1.2304   0.04891   0.04488  -0.0259   0.0016   1.0000
  12.500   1.2189   0.05314   0.04932  -0.0258   0.0016   1.0000
  12.750   1.2140   0.05668   0.05303  -0.0263   0.0016   1.0000
  13.000   1.2038   0.06133   0.05786  -0.0276   0.0015   1.0000
  13.250   1.1898   0.06697   0.06368  -0.0298   0.0015   1.0000
  13.500   1.1693   0.07435   0.07127  -0.0333   0.0016   1.0000
  13.750   1.1576   0.08076   0.07784  -0.0369   0.0016   1.0000
  14.000   1.1424   0.08851   0.08575  -0.0416   0.0015   1.0000
  14.250   1.1271   0.09687   0.09426  -0.0467   0.0015   1.0000
  14.500   1.0995   0.10874   0.10630  -0.0539   0.0017   1.0000
  14.750   1.0866   0.11751   0.11518  -0.0591   0.0016   1.0000
  15.000   1.0617   0.12965   0.12745  -0.0661   0.0017   1.0000
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